Results
85-03-02: 85-03-02 ROLLADEN-SCHNEIDER FLUGZEUGBAU GmbH: Amendment 39-4996. Applies to Models LS4 and LS4a sailplanes, serial numbers up to 4340 inclusive, certificated in any category. Compliance is required prior to further flight, after the effective date of this AD, unless already accomplished. To prevent possible jamming of lower air brake blade, accomplish the following: (a) Assemble the sailplane. (b) With air brakes fully extended, measure overlap between the bottom edge of the lower blade of the air brake and wing skin lip. If the distance is less than five millimeters (0.2 inches), proceed according to subparagraph (c) below. If distance is greater than five millimeters, no further action is required. (c) (1) Retract air brakes until the overlap distance is at least five millimeters (0.2 inches) at both wing positions. (2) Measure extended height of the air brake at the inboard edge. If the distance is less than 150 millimeters (5.91 inches) contactthe manufacturer and incorporate any necessary modifications. (3) Install stop fitting P/N 4R6-15, using steel blind rivet (4mm dia. x 10mm lg.) on air brake pushrod in cockpit such that main bulkhead reduces travel to yield minimum overlap specified in paragraph (b). NOTE: Rolladen-Schneider TB No. 4020, dated September 1, 1983, applies to this AD. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium 09667-1011; telephone 513.38.30. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. This amendment becomes effective on February 25, 1985.
2008-24-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During scheduled maintenance inspection, a bolt which connects the PCU (power control unit) to the elevator surface was found fractured in the assembly. Further inspection of the assembly revealed that the bearing on the PCU rod end had seized, which resulted in damage to the attachment fitting bushing and fracture of the bolt. Inspection of other in-service airplanes revealed two more seized PCU attachment joints. However, except seizure, no fractured bolt was found on these airplanes. Failure of the bolts in both PCUs on one side could result in disconnection of the elevator control surface which would lead to flutter and loss of the aircraft. * * ** * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2008-24-08: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800 and -900 series airplanes. This AD requires an inspection of the escape slides for the forward and aft entry and service doors to determine the part number and service bulletin number stenciled on the escape slide girt, and modification of the escape slide assemblies. This AD also requires concurrent modification of the escape slide latch assemblies; concurrent inspection of the escape slides to determine the part number and service bulletin number stenciled on the escape slide girts, and replacement of the trigger housing on the regulator valve with an improved trigger housing if necessary; and concurrent replacement of the rod in the pilot valve regulator with a new, improved rod; as applicable. This AD results from reports that certain escape slides did not automatically inflate when deployed or after the manual inflation cable was pulled. We are issuing this AD to preventfailure of an escape slide to inflate when deployed, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or crewmembers.
83-26-03: 83-26-03 BF GOODRICH: Amendment 39-4811. Applies to the following aircraft tires: \n\n\t1.\t17.5x5.75-8, 12PR, 210MPH, P/N 038-627, S/N 3224A-XXXXX, and \n\n\t2.\t18x5.5, 10PR, 210MPH, P/N 033-631, S/N 3215A-XXXXX through 3217A-XXXXX. \n\n\tThese tires are eligible for, but not limited to use on, all Gates Learjet models and Fairchild Swearingen Model SA226-TC airplanes. \n\n\tCompliance: Required prior to next takeoff, unless already accomplished. \n\n\tTo avoid tread loss and possible subsequent tire failure, accomplish the following: \n\n\tRemove the applicable part number and serial number BF Goodrich tires from the aircraft and either destroy them or return them to BF Goodrich for destruction. Cutting the tire carcass is an approved means of destruction. \n\n\tNOTE: The serial numbers of the tires are interpreted as follows: \n\n\n\n\t\n\tThis amendment becomes effective on February 21, 1984, to all persons except those to whom it has already been made effective by priority letter from the FAA dated December 23, 1983, and is identified as AD 83-26-03.
85-03-07: 85-03-07 AIRBUS INDUSTRIE: Amendment 39-4999. Applies to Model A300 B2 and B4 series airplanes, serial numbers as listed in the Airbus Industrie Service Bulletin A300-28-039, Revision 2, dated December 17, 1981, certificated in all categories. To prevent rupture of the feeder fuel lines located inside the engine pylons, accomplish the following, unless previously accomplished: A. Prior to the accumulation of 4,000 hours total time in service or within the next 120 days after the effective date of this AD, whichever occurs later, install an additional clamp on the feeder fuel line located inside each engine pylon in accordance with the accomplishment instructions of the service bulletin. B. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective March 11, 1985.
2008-22-09: We are adopting a new airworthiness directive (AD) for all Boeing Model 747SP series airplanes. This AD requires repetitive lubrication of the rudder tab hinges and repetitive replacement of the rudder tab control rods. This AD results from reports of freeplay- induced vibration on the control surfaces on Boeing Model 727, 737, 757, and 767 airplanes. We are issuing this AD to prevent damage to the control surface structure during flight, which could result in loss of control of the airplane.
2008-09-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. We are issuing this AD to require actionsto correct the unsafe condition on these products.
2008-22-24: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed low pressure compressor (LPC) fan blade roots on-wing and during overhaul, and relubrication according to accumulated life cycles. Also, that AD introduces application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions but adds compliance paragraphs to relax the compliance schedule for repetitive inspections for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met. This AD also relaxes the initial compliance threshold by extending the cycles at which an initial inspection is required. This AD results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211-72-C879, Revision 5 and Revision 6, that introduced a relaxed repetitive compliance schedule for fan blades operating within RB211-535E4 flight profiles A and B, if certain requirements are met, and introduced a relaxed initial compliance threshold. We are issuing this AD to detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
87-06-05: 87-06-05 MCDONNELL DOUGLAS: Amendment 39-5572. Applies to McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F, -40, and KC-10A (Military) series airplanes, certificated in any category, equipped with Aircraft Mechanics, Inc., crew seats model numbers, 1056, 1057, and 1058, having serial numbers 001 through 907 and 911. Compliance required as indicated, unless previously accomplished. \n\n\tTo preclude the potential of damage to crew seat life vests, accomplish the following: \n\n\tA.\tWithin 12 months after the effective date of this AD, inspect the life vest. If any signs of chafing are found, replace before further flight with a serviceable unit. \n\n\tB.\tWithin 12 months after the effective date of this AD, modify the crew seat in accordance with the accomplishment instructions of Aircraft Mechanics, Inc., Service Bulletin 25-DC-10/678-24, dated May 20, 1984, or later revision approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region.C.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-L65 (54-60). These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. \n\n\tThis Amendment becomes effective April 2, 1987.
87-18-10: 87-18-10 INTREPRINDEREA DE CONSTRUCTII AERONAUTICE: Amendment 39- 5695. Applies to Model IS-28B2 gliders through serial number 160 inclusive certificated in any category. Compliance is required as indicated unless already accomplished. To prevent the failure of the aileron control levers and forks which could result in the glider becoming uncontrollable, accomplish the following: (a) Within the next 5 hours time-in-service after the effective date of this AD unless compliance with paragraph (c) has been accomplished, visually inspect the aileron control levers P/N 30AD.02.028 and aluminum NIA 181-2 forks using a 10 power or greater magnifying glass for cracks or deformation. (b) If a cracked or deformed part is found during the inspection required by paragraph (a) of this AD, before further flight, replace the aileron control levers and forks with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with the accomplishment instructions of Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985. NOTE: The manufacturer has assigned the same part number to the new design aileron lever as the original design aileron lever. The new lever can be identified by measuring the length of the section which is reduced in thickness on the longer arm of the aileron lever. The new design aileron lever is reduced in thickness 42mm from the end of the longer arm whereas the old design aileron lever is reduced in thickness 27mm from the end of the longer arm. (c) Prior to September 30, 1987, replace any aileron control system levers and forks not replaced in accordance with paragraph (b) of this AD, with serviceable levers and forks, new design P/N 30AD.02.028 lever and steel NIA 201-2 fork, in accordance with Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14 dated August 20, 1985. NOTE: The aileron levers removed from service should be destroyed or disfigured to prevent reuse. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Brussels Aircraft Certification Office, AEU-100, Europe, Africa, and Middle East Office, Federal Aviation Administration, c/o American Embassy, 15 Rue de la Loi B-1040, Brussels, Belgium; telephone 513.38.30 ext. 2710, or the Manager, Federal Aviation Administration, New England Region, Aircraft Certification Division, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York 11581; telephone 516-791-6680. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Brussels Aircraft Certification Office, or the Manager, New York Aircraft Certification Office, may adjust the compliance time specified in this AD. Intreprinderea De Constructii Aeronautice Service Bulletin No. IS-28B2-E0-14, dated August 20, 1985, identified and described in this document, is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received this document from the manufacturer may obtain copies upon request to Sprague Aviation Incorporated, 699 Linwood, Vacaville, California 95688. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, Rules Docket 87-ANE-01 between the hours of 8:00 a.m. and 4:30 p.m.; Monday thru Friday, except federal holidays. This amendment becomes effective on September 3, 1987.